CUSTOMER SERVICES DIRECTO RATE

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX FRANCE

TELEPHONE + 33 (0)5 61 93 33 33



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- AOT

AOT ref: A32L003

- 14 Page 1 of 5 Date: 10 Mar 2014

© AIRBUS S.A.S. 2014 . ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT SUBJECT: ATA 32

– MAIN LANDING GEAR (MLG) SIDESTAY UPPER CARDAN PIN INSPECTION

AIRCRAFT TYPE: A 330 , A 340.

OUR REF.: A32L003

- 14 dated 10 Mar 2014

.

1. AIRCRAFT AFFECTED

A330

- 200/300 and A340

- 200/300 fitted with :

- Basic MLG (PN 20125 series) with sidestay upper c ardan pin PN 201267202

- Growth MLG ( PN 20149 series) with sidestay upper cardan pin PN 201483202

.

Note: aircraft fitted with Enhanced MLG (PN 10

- 210 series) are not subject to the inspection detailed

in this AOT.

2. REFERENCED DOCUMENTATION

2.1 APPENDIX

- Appendix 1 MLG Sidestay c ardan pin clearances

- Appendix 2 Inspection reporting sheet

- Appendix 3 Flow Chart

2.2 REFERENCES

- Ref. 1: AMM 32

- 11

- 16

- 420

- 053

- Ref. 2: IPC 32

- 11

- 18

- 01

- Ref. 3: MBD CMM 32

- 11

- 91, Figure 1

- Ref. 4: MBD CMM 32

- 1 2

- 07 , Figure 1

- Ref. 5 : AMM 32

- 11

- 18

- 0 00

- 801

- A & 32

- 11

- 18

- 400

- 801

- A

3. REASON

The purpose of this AOT is to request operators to accomplish an inspection on the MLG sidestay upper cardan pin.

3.1 FACTS

An A330 fitted with Basic MLG was rolling out after landing when it experienced a nose wheel steering

fault (unrelated to the migration detailed in this document) , which resulted in the crew stopping the aircraft on the taxiway after vacating the runway.

Inspection identified that the RH MLG sidestay u pper c ardan p in (Ref. 2) had migrated out of position.

The sidestay upper cardan nut and retainer were found in t he landing gear bay detached from the upper
cardan pin . The n ut and the retainer were still bolted together.CUSTOMER SERVICES DIRECTO RATE

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX FRANCE

TELEPHONE + 33 (0)5 61 93 33 33



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© AIRBUS S.A.S. 2014 . ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT 3.2 CONSEQUENCES

The loss of the sidestay cardan pin locking function (loss of nut) could lead to a complete migration of the sidestay upper cardan pin and a disconnection of the sidestay upper arm from the aircraft structure. This could therefore lead to a landing gear collapse.

3.3 AIM

The aim of this AOT is to request o perators to :

- Perform a Detailed Inspection (DI) of the upper c ardan pin and nut and retainer

- Perform a Gap check of the upper c ardan pin and nut

The accomplishment of these inspections is requested on aircraft fitted with MLG sidestay upper cardan pins which have accumulated more than 8 years since first overhaul and which have not yet gon e through their second overhaul, at the issue date of this AOT.

4 . SHORT TERM ACTION

4.1 PLANNING AND MANPOWER

4.1.1 ACCOMPLISHMENT TIMESCALE

A330

- 200/300 and A340

- 200/300 fitted with MLG sidestay upper cardan pins PN 201267202 & 201483202 which have accumulated more than 8 years since first overhaul and which have not yet gone through their second overhaul

, at the issue date of this AOT

, are subject to the following inspections:

1. The accomplishment of the DI mentioned in Para 4.2.2 .1 must be performed no later than 30 days after the issuance of this AOT.

2. Repeat the DI mentioned in Para 4.2.2 .1 every 10 days until a gap check as per Para 4.2.2. 2 is performed.

3. Perform a gap check as mentioned in Para 4.2.2 .2 no later than 4 months after issuance of

this AOT.

When a gap check is performed, the results (including nil findings) must be reported to Airbus using the proforma provided in Appendix 2 of this AOT

.

4.2 DESCRIPTION

4.2.1 ACCESS

The Detailed Inspection and the gap check called for in this AOT do not require special access, equipment, or aircraft jacking.

4.2.2 INSPECTION REQUIREMENTS

- 4.2.2.1 Detailed Inspection:CUSTOMER SERVICES DIRECTO RATE

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX FRANCE

TELEPHONE + 33 (0)5 61 93 33 33



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AOT ref: A32L003

- 14 Page 3 of 5 Date: 10 Mar 2014

© AIRBUS S.A.S. 2014 . ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT Carry out a DI of the Upper Cardan Pin and retainer and nut assembly, ensuring that there is no pin chrome visible inboard of the wing rear spar fitting lug, and that the nut and locking device (including bolts and washers), are still in place . There is no requirement to remove the nut, pin and retainer at this stage.

Migrated upper cardan pin.

- 4.2.2.2 Gap check:

WARNING: MAKE SURE THAT THE SAFETY DEVICES AND THE WARNING NOTICES

ARE IN A POSITION BEFORE YOU START A TASK ON OR NEAR:

 THE FLIGHT CONTROLS

 THE FLIGHT CONTROL SURFACES

 THE LANDING GEAR AND THE RELATED DOORS

 COMPONENTS THAT MOVE

MOVEMENT OF COMPONENTS CAN KILL OR INJURE PERSONS.

(a) En sure that no gap exists between wing rear spar fitting lugs (outboard & inboard lugs)

and their installed bush flanges (no bush migration). Refer to Appendix 1 and report in Appendix 2.

(b) Measure MLG Cardan Pin clearance dimensions X plus Y, which must be no greater than 0.6 mm (0.0236 in.). Take largest gap measured at 3 points circumferentially. Refer to Appendix 1 or to Ref.1 Fig ‘Cardan Pin

- Clearances ’ SHEET 1.

(c) Repeat Gap check on the opposite side landing gear

.

(d) Record all measurements.

(e) Report findings including measured gap dimensions (refer to Appendix 2)

Example:

Dim X ( maximum gap measured between head of cardan pin and bush = 0.2 mm
Dim Y ( maximum gap measured between nut and bush ) = 0.35mm Total Gap = Dim X + Dim Y = 0.55mm. Recorded gap measurement = 0.55mm.CUSTOMER SERVICES DIRECTO RATE

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX FRANCE

TELEPHONE + 33 (0)5 61 93 33 33



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© AIRBUS S.A.S. 2014 . ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT 4.2.3 FINDINGS

For the DI:

- If pin chrome found visible inboard of the wing rear spar fitting lug: Before next flight, replace the cardan pin assembly ( in accordance with Ref.5 )

. R eport to Airbus within 30 days

.

For the Gap check:

- If measured gap (X+Y) is ≥ 1.5 mm : Before next flig ht, replace the cardan pin assembly (in accordance with Ref.5) . Report to Airbus within 30 days

.

- If measured gap (X+Y) is >0.6 mm but <1.5 mm: Before next flight, provide Airbus with the following information:

o Completed proforma provided in Appendix 2 of this AOT

o P hotographs of cardan pin head/wing/bush interfaces and nut/bush/wing interfaces( if possible provide ‘macro level’ detail shots of nut and pin face)

o M ovement Traceability Sheet (MTS) for the affected cardan pin

The aircraft c an then continue operations for a 30 days grace period whilst Airbus review the information provided. Airbus will consult with the operator during this grace period to request specific actions in the event that the findings are judged to be abnormal.

- If measu red gap (X+Y) is ≤ 0.6 mm: report gap to Airbus within 30 days . No further action required.

When a gap check is performed, the results (including nil findings) must be reported to Airbus using the proforma provided in Appendix 2 of this AOT

.

4.3 SPARES AND TOOLING

In case of part ’ s replacement, please refer to Ref. 2 for procurable part numbers

.

In addition, refer to the applicable MB D C MM as follows:

- For Basic MLG: refer to Ref.3

- For Growth MLG: refer to Ref.4

Should spares be required, they will be available from MBD local distribution centres and allocated on a case by case basis.

5. FURTHER INFORMATION

It is anticipated that this AOT will be rendered mandatory by issuance of an EASA Airworthiness Directive (AD).

6. AOT APPROVAL

The technical content of this document is approved under the authority of DOA nr. EASA.21J.031.

7. REPORTINGCUSTOMER SERVICES DIRECTO RATE

1 ROND POINT MAURICE BELLONTE

31707 BLAGNAC CEDEX FRANCE

TELEPHONE + 33 (0)5 61 93 33 33



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AOT ref: A32L003

- 14 Page 5 of 5 Date: 10 Mar 2014

© AIRBUS S.A.S. 2014 . ALL RIGHTS RESERVED. CONFIDENTIAL AND PROPRIETARY DOCUMENT Questions about this AOT and inspection results with or without findings are to be sent to Airbus

Customer Services engineering as soon as possible after the AOT application, to the attention of:

Philippe KERANGUEVEN

Customer Services

– SEEL1 Phone : +33 (0) 5 67 19 18 42 Fax : +33 (0) 5 67 19 12 05 Email: philippe.kerangueven@airbus.com

Best Regards,

Jean

- Luc MOUYSSET

VICE PRESIDENT ENGINEERING SUPPORT

CUSTOMER SERVICES Philippe GOURDON

V ICE PRESIDENT A330/A340 PROGRAMME

C USTOMER SERVICES DIRECTORATE